Variable phase turbine apparatus

ABSTRACT

Variable phase turbine apparatus comprising, in combination a rotatably driven load structure, defining an axis, confinement means forming a fluid flow passage extending generally axially and adjacent said load structure, a turbine operatively connected to said load structure, to transmit rotary drive thereto, two-phase flow nozzle means receiving pressurized flow via said passage, and directing flow of fluid from said passage, expanded in the nozzle means, at the turbine to rotate the turbine, the nozzle means configured to expand flow consisting of two or more of the following phases:
         v) gas   vi) liquid   vii) gas and liquid mixture   viii) supercritical gas and liquid mixture, and with efficient conversion of enthalpy.

BACKGROUND OF THE INVENTION

This invention relates generally to fluid driven turbines and moregenerally to those having a variable phase fluid driving the turbine.The variable phase may be a mixture of a gas and liquid phase; or asupercritical phase; or a supercritical phase that transitions withinthe device to a mixture of gas and liquid or to a pure gaseous phase; ora liquid phase that transitions within the device to a mixture of gasand liquid; or a liquid phase that transitions within the device to amixture of gas and liquid and then subsequently transitions also withinthe device to a pure gaseous phase. Apparatus that efficiently convertsall these fluid combinations is necessary for turbines and heat enginesthat optimize the production of power from heat energy, and frompressure energy in industrial processes.

Turbines are widely used in industry to convert energy in liquid streamsor gas streams to shaft power. Less common, but also used are turbinesto convert energy in two-phase (gas and liquid) streams to shaft power.A further requirement can be the conversion of supercritical streamsand/or streams that transition from a single phase to two-phase streams.Still further applications exist for the conversion of energy intwo-phase streams that transition to a gaseous stream.

At present, the turbines for each type of stream are unique to thatstream. That is, a turbine configured to be gas driven is not readilyusable for liquid or two-phase flow. For example, attempts to use radialinflow gas turbines for two-phase flow have resulted in poor performanceand damage because the directions of centrifugal body forces are such asto throw liquid backwards into the nozzle blades.

Applicants herein believe that no efficient turbine design exists forthe case of a two-phase stream which transitions to a gaseous streamwithin the turbine, or for a supercritical stream which transitions to atwo-phase stream within the turbine or for a supercritical stream whichtransitions to a two-phase stream that subsequently transitions to agaseous stream within the turbine. These instances will be referred toherein as “Transition Flows”.

Certain applications for turbines require the use of different types offluid streams for differing conditions, as well as the use of TransitionFlows. For example, a low temperature geothermal power system mayrequire use of a gas stream or a two-phase flow stream, depending uponthe temperature and working fluid used in the power producing cycle. Tomaximize power production, the geothermal power system may require aturbine to start in the supercritical flow regime and handle thetransition to a two-phase stream within the turbine.

At present, to provide an efficient power conversion system, a new orspecialized turbine must be designed, manufactured and qualified foreach application. This is costly and time consuming and reducesflexibility, if the thermal characteristics of a given applicationchange with time. There is need for an efficient turbine that can bedriven by gas, or liquid or two-phase fluid flow. There is also a needfor an efficient turbine that can be driven by Transition Flows.

SUMMARY OF THE INVENTION

It is a major object of the invention to provide a solution or solutionsto the above described problems and needs.

An object of the present invention is to provide an improved turbinecharacterized by one or more of the following:

-   -   a) use for two-phase flow to generate power efficiently;    -   b) use for Transition Flow to generate power efficiently;    -   c) use for either gas, liquid, two-phase or Transition Flow,        with minor adjustments to a component part, or parts, such        adjustments typically concerning nozzle inserts and blade        adjustments.

A further object is to provide a turbine that can operate efficientlywith changes in input two-phase flow stream or Transition Flow streamparameters, such as inlet pressure or flow rate.

Yet another object is to provide a turbine that will separate liquidfrom the gas stream leaving the turbine to maximize the effectiveness ofany downstream heat rejection or separation equipment.

An added object is provision of a turbine and electric generatorassembly that can be used for either gas, liquid, two-phase flow orTransition Flow, and that requires no external seals, referred to hereinas the Variable Phase Turbine Generator Assembly (VPTGA).

Another object is provision of a turbine, electric generator and pumpassembly that can be used for either gas, liquid or two-phase flow withno external seals, referred to herein as the Variable Phase TurbineGenerator Pump Assembly (VPTGPA).

Another object is provision of a compressor means connected to the shaftof the VPT to utilize the shaft power to add compression energy to aseparate gas stream from a process, or to the separated gaseous streamfrom the exit of the VPT.

Another object of the invention is provision of a pump means connectedto the shaft of the VPT to use the power created by the VPT to pumpanother stream.

An additional object in provision of variable phase turbine apparatusthat comprises:

a) nozzle means operable to discharge a fluid medium of liquid,supercritical fluid or a mixture of liquid and gas with conversion ofmedium enthalpy to kinetic energy in a directed stream of a mixture ofgas and liquid, supercritical fluid or pure gas, said directed streamcharacterized by the chemical composition of the fluid medium and thethermodynamic conditions of the enthalpy conversion process, said nozzlemeans directing the flow at blade means, for displacing said blademeans,

b) the blade means configured to maximize the conversion of the kineticenergy of said directed stream into torque acting upon rotor meanscarrying said blades,

c) said rotor means to which said blades are attached transmitting thetorque to a shaft to which the rotor and a load are attached,

d) casing means configured to confine and direct the medium and whichcontains bearings and seals to enable the shaft to transmit the torque,and

e) shroud means configured to prevent liquid which has transferredkinetic energy to the blades from contacting the casing and from beingre-directed to contact the moving blades, causing losses in torque.

A further object is to provide for adjusting turbine nozzle flow throughconfiguration as a function of input pressurized fluid phasecomposition, to maximize kinetic energy, minimize particle sizes, oroptimize the combination of kinetic energy and particle size of nozzledischarge to turbine blades.

As will be seen, means may be provided at one end of the turbine andresponsive to positioning of nozzle pintle means to vary the flow areaof the nozzle means by axial translation of said pintle means, tomaximize kinetic energy minimize particle sizes, or optimize thecombination of kinetic energy and particle size leaving the nozzlemeans, for two or more flow phases.

These and other objects and advantages of the invention, as well as thedetails of an illustrative embodiment, will be more fully understoodfrom the following specification and the drawings.

DRAWING DESCRIPTION

FIG. 1 is a section taken through a variable phase nozzle;

FIG. 2 is a block diagram as respects nozzle option;

FIG. 3 is a comparison of two nozzle pressure profiles and the resultingbulk velocities and particle sizes;

FIG. 4 is a section taken through preferred variable phase turbineapparatus incorporating a hermetically enclosed electrical generator andwith variable nozzles; and FIGS. 4 a, 4 b and 4 c are enlargements;

FIG. 5 is a section taken through turbine apparatus, showing anotherapplication;

FIG. 6 is a section through a variable phase turbine compressor;

FIGS. 7 and 8 are views that show dual nozzle rows, as may be employedin the FIG. 4 apparatus;

FIG. 9 is a section showing full admission nozzle; and

FIG. 10 is a perspective view showing vanes of full admission nozzles.

DETAILED DESCRIPTION

A representative variable phase nozzle 100 is shown in FIG. 1. A liquidenters the nozzle with low velocity and high pressure at 1. The pressureis reduced in a converging section 101 resulting in the flashing of theliquid to vapor. The vapor formation can occur as a central pocket, 6.

Efficient acceleration of the liquid phase by a gas phase in the nozzlerequires the mixing of the liquid phase with the gas phase. Should theliquid be predominately on the nozzle wall and the gas remain as acentral pocket, the coupling of the gas shear forces with the liquid isinefficient. To promote removal of the liquid from the wall a plate, 7,is shown as provided to remove the liquid from the wall and mix theliquid with the gas. Plate 7 has an opening defined by radially inwardlyconcave wall 7 a.

Further acceleration of the liquid is achieved by lowering the pressurein a converging section. The shear forces of the accelerating gas resultin a breakup of the initially large diameter droplets, 8, to smallerdiameter droplets at 9. The smaller diameters result in greater surfacearea and an improved coupling of the gas with the liquid. Depending uponthe pressure ratio, the velocity of the mixture can reach sonic velocityas at a reduced area throat, 3. In this case the nozzle area isincreased as at 4, resulting in the flow leaving the nozzle at 5, beingsupersonic. Typically, the angular displacement of each blade leadingedge from the perpendicular to the axis of the nozzle means of between 1degree to 15 degrees counter to the rotational direction. Also, for adirected stream of a mixture of liquid and gas, the blading means has aninitial section with a gradual angle optimized to minimize the sum ofmomentum losses and friction losses when the stream impacts the bladesurface. Also, for the case of a directed stream of a mixture of liquidand gas, the blading means is configured to increase the hydraulicdiameter of liquid flowing on the surface, thereby reducing frictionlosses. Also, for the case of a directed stream of a mixture of gas andliquid, the blade means is configured to produce a trajectory of liquidleaving the surface of the blades thereby to impart a tangentialcomponent of the velocity relative to the shaft centerline, causing theliquid to be separated from the gas phase and to enter a passageprovided in the casing to capture the liquid. Alternatively, the methodof operation includes adjusting nozzle flow through configuration as afunction, or coded function of input fluid phase composition, tooptimize kinetic energy and particle size in nozzle discharge incidenton turbine blades.

A design code or program may be used to control an actuator 160 toaxially control a pintle 10 (see FIG. 4 a) to minimize the droplet sizeand to maximize nozzle efficiency. Minimization of the droplet size isimportant to increase the surface area, to promote heat and masstransfer within the nozzle and to produce a homogeneous fluid that willmaximize the efficiency of turbine blading upon which the fluid acts.The code can analyze and design the flow in nozzles for single phase,two-phase, supercritical flow or any combination. See FIG. 2 functionalblock diagram. The code enables the determination of the optimumpressure profile to maximize the efficiency of expansion. See sensor 161to sample droplet size, with feedback signaling at 162 to the programmedcontroller 163.

For a two-phase nozzle, a major loss is the slip. Slip is defined as thevelocity difference between the gas phase and the liquid phase:

S=V _(g) −V ₁

where S=slip

-   -   V_(g)=gas velocity    -   V₁=liquid velocity        Slip occurs as a result of the pressure gradient and droplet        size. However, the droplet size, in turn, is determined by the        slip and surface tension:

D=12 σ/ρ _(g) S ²

where σ=surface tension

-   -   ρ_(g)=density of gas        Smaller droplets result in higher surface area per unit mass,        which results in lower slip and less loss. However, high values        of slip are needed to produce small droplets. The usual design        approach is to use a gradual pressure gradient to minimize the        difference between the gas velocity and the liquid velocity at        any point. However, this design approach can result in a value        of the averaged velocity which is lower than the optimum value.

An additional consideration is that making many small droplets requiresmore energy, than making fewer large droplets. Thus, there is atrade-off between optimizing particle size, and therefore slip, andoptimizing kinetic energy at the nozzle exit. It is, therefore, crucialto predict and configure the nozzle to optimize the flow going to theturbine rotor. The nozzle code methodology, as in FIG. 2, is implementedto achieve this.

In order to minimize particle size and optimize averaged velocity at theexit of the nozzle the pressure gradient, and hence slip, is preferablymaximized at the inlet regions of the nozzle. This unexpected result isa consequence of using the large slip to create the smallest possibledroplet size, in a region where the overall kinetic energy is small. Anozzle, representative of this phenomenon, is illustrated in FIG. 1. Theloss, while locally large in comparison with the local kinetic energy,is small compared to the final kinetic energy of the nozzle. Thus slipand losses are minimized in the regions of the nozzle having highkinetic energy.

FIG. 2 illustrates the method used, the pressure profile being varied asan independent input parameter to the nozzle code until the optimumdesign is determined.

FIG. 3 illustrates an application of the design method to the two-phasenozzle of FIG. 1. As shown, the droplet size is increased from 3 micronsto 4 microns. The resulting slip is correspondingly increased in thehigh velocity downstream regions of the nozzle resulting in an increasein the averaged exit velocity, 10 a, from 719 feet per second for thenozzle configuration of FIG. 1 to 730 ft/s for the optimized nozzle.This surprising result stems from reduced friction losses as well asreduced droplet breakup energy required. Because the difference indroplet size is small, the increased velocity is more important.Variations in flow to the nozzle can be controlled with a throttlingvalve. However, reducing the flow using a valve causes a loss inefficiency. To enable efficient operation at part flow, an adjustablecenter body with a special contour, “the pintle”, is used, and shapedwith taper, as shown.

FIG. 4 a shows the use and operation of such a pintle 10, having asmoothly decreasing cross sectional area in the axial direction towardits pointed tip. As the pintle is translated in the direction of thethroat, 16, a gradual decrease in flow area from the nozzle inlet, 18,to the throat 18 a results. This action enables lower flow rates toefficiently accelerate to the same velocity at the throat at the designflow rate with the full throat area available. The pintle has a radiallyoutwardly facing concave side wall that faces toward receptacle wall 18b that tapers toward throat 16.

As also seen in FIG. 4 a, pintle is attached to a sliding rod, 13, whichin turn is attached to actuator piston, 14, which has a sliding sealwith the housing, 19. In the variation shown, a spring, 12, iscompressed by the action of a high pressure fluid, 15, admitted to theface of the piston. The force from the piston causes the pintle to havea closing or area reduction action. In this version, the throat area isnormally open. The piston and high pressure fluid can be provided on thereverse side of the spring to produce a normally closed throat area. Thearrangement depends upon process requirements.

Expansion of the flow to the proper pressure in the throat results in anefficient acceleration of the flow to that point. Expansion of the flowfrom the throat to the nozzle causes some over-expansion losses, whichhave been found to be minimized when two fluid phases are present.Expansion in the nozzle of a mixture of a gas and liquid phase; or of asupercritical phase; or of a pure gaseous phase; or of a liquid phasethat transitions to a mixture of gas and liquid; or a liquid phase thattransitions to a mixture of gas and liquid and then subsequentlytransitions to a pure gaseous phase produces a well collimated nozzleexit stream at 19′, of liquid and gas or dry gas having kinetic energy.

The nozzle exit stream is subsequently directed onto rotating blades,20, attached to a blade carrying rotor, 21, which is in turn attached toaxially extending tubular shaft, 22, supported by bearings, 25. Thekinetic energy of the nozzle exit stream is transferred to the bladesproducing a torque on the rotor and shaft. The design of the bladeprofile depends upon whether the nozzle exit stream is a liquid and gasmixture, or a dry gas. If the nozzle exit stream is a liquid and gasmixture, the design of the blade profile further depends upon thedroplet size.

The flow 23 leaving the blades passes to the outlet, 24. If the flowleaving the blades is a liquid and gas mixture, sufficient kineticenergy can be left to produce swirl causing separation of the liquidfrom the gas with an internal separator.

The variable phase turbine generator apparatus version shown in FIG. 4is configured for use with an electrically non-conducting fluid, such asliquefied natural gas or liquid ethylene or a refrigerant. The shaft isattached to a generator rotor, 26, the rotation of which causesgeneration of electric power in a stator, 27. See FIG. 4 b and 4. Poweris removed by a conductor 27 a and transmitted at 41 a through thecasing, 41, using an insulating feedthrough means 29. Nozzle 180 extendsat one end of the generator, and terminates at exit 19′ offset from therotor axis 35 a, adjacent the circular path of rotation of the blades.Annular body 105 supports the casing 41 as well as the angularlydirected nozzle.

The fluid is supplied to the VPT through an inlet port, 30. The fluid isdirected through an annulus, 44, to the nozzle inlets, 18, exposed to44. A highly compact and efficient design is thereby achieved.

A portion of the fluid flow is diverted through a port, 31, in an innercasing, 40 near entrance 30 a to outer casing 41. Casing 40 supports thegenerator casing 41 and bearings. A portion of the diverted fluid flowsto the bearing cavities, 33, and subsequently through the bearings, toprovide lubrication and heat removal. The fluid leaving the bearings isdischarged through orifices, 34, which communicate with passage, 35,within the shaft. That passage endwise communicates with the pressure ofthe fluid leaving the turbine, 23, which is lower than the pressure ofthe fluid entering the nozzles 18, and that diverted, 31. The passage 35within the shaft communicates with the upper end of the shaft, 39,opposite the turbine rotor, resulting in a low pressure at the shaftend. Nozzles 18 are spaced annularly about the shaft axis 35 a.

Another portion of the diverted fluid flows through the gap 32 betweenthe generator rotor and the stator, removing heat generated byelectrical and frictional losses. This portion of the fluid flowsthrough the bottom bearing, providing lubrication and heat removalbefore flowing at 34 into the low pressure passage 35 within the shaft.

The weight of the shaft and rotor and the frictional forces due to thefluid flowing downwardly in the gap would produce a downward or axialforce on the bearings. FIG. 5 shows the method of force alleviation,with another portion of the diverted fluid flowing through the gap, 47,formed by a throttling disc 36 attached to the shaft and a stationarymember, 45, attached to the inner casing. The downward force has atendency to move the shaft in the downward direction opening the gap 47,causing the loss of throttling and a high pressure in the cavity, 37,below the face of another disc, 38, attached to the shaft. The highpressure and force on the upper disc causes the shaft to move upward andthe gap to close, resulting in a throttling action, reducing thepressure and force on the face of the upper disc until the upward forcejust balances the downward force. At this point there is no net axialforce on the bearings and the balance is automatically maintained.

Shroud 110 below blades 20 and body 105 prevents discharged liquid fromcontacting casing 41 and from redirection to contact the moving bladescausing losses in torque.

Another application is to use the variable phase turbine to drive acompressor. FIG. 5 shows a single stage centrifugal chiller driven bythe shaft, 61, from the VPT, which has no external seals. Flow, 56,enters the compressor and is increased in pressure by the moving vanes,47. A further increase in pressure occurs in the diffuser, 57. The flowis then collected in the volute, 58, and leaves through a port 59. Thefluid compressed can be the same as, or different from, the fluidoperating the Variable Phase Turbine.

A portion of the fluid operating the variable phase turbine, is admittedthrough a pipe, 48, to a cavity, 49. The fluid flows through thebearings, 50, to lubricate them, and into passages, 51, in the shaft,61. The fluid then flows through a central passage, 53, in the shaft andmixes with the flow, 54, leaving the moving blades. The mixed flow, 55,leaves the structure through a port. The VPT nozzle structure, 200, andblading 201, is generally the same as in FIGS. 1-4.

Seals, 52, are provided to prevent the fluid operating the variablePhase Turbine, from mixing with the compressor fluid.

A combined variable phase turbine and multistage compressor is shown inFIG. 6. The VPT bladed rotor, 62, transfers torque to a shaft, 63,causing compressor rotors, 64, attached to the shaft to rotate. Theshaft is supported on bearings, 65.

The vapor to be compressed enters the compressor casing, 76, through aport, 77. The vapor is compressed by the first rotor 64 and dischargedinto a stationary diffuser, 79, where the pressure of the vapor isincreased further. The vapor then flows into a cross-over channel, 80,and is ducted inwardly at 81, to the inlet of the next rotor 64. Theprocess continues to the last rotor where, after the vapor is dischargedinto the last diffuser and the pressure increased, the vapor leaves thecasing through a port, 78, and flows to the process.

A portion, 69, of the liquid, 82, driving the VPT is diverted tochambers, 83, in proximity to the bearings. The liquid flows through thebearings to provide lubrication and cooling. Seals, 68, are provided toisolate the liquid from the vapor being compressed. The liquid used forbearing lubrication discharges through a passage or passages 70, into apassage, 71, in the shaft and subsequently is endwise discharged at 72,into the exhaust region of the VPT rotor, and mixes with the flowleaving the blades, 73.

The pressure difference across the compressor rotors typically producesan axial force on the bearings. To counteract this force, anotherportion, 83, of the diverted fluid flows through the gap, 74, formed bya throttling disc, 84, attached to the shaft and a stationary member,85, attached to the casing. The axial force from the pressure differencehas a tendency to move the shaft, opening the gap, causing loss ofthrottling and a high pressure in the cavity 86, below the face ofanother disc, 87, attached to the shaft. The high pressure and force onthe upper disc causes the shaft to move opposite to the pressuredifference and the gap to close, resulting in a throttling action,reducing the pressure and force on the face of the second disc until theforce on the disc just balances the pressure force. At this point thereis no net axial force on the bearings and the balance is automaticallymaintained.

The liquid flowing through the disc enters a chamber 75, and isdischarged through the central passage, 71, in the shaft to the exit ofthe VPT rotor.

For a given rotor speed and nozzle exit velocity there is a limit to theflowrate that can be provided to the turbine by a single row ofaxisymmetric nozzles. That limit is:

${{maximum}\mspace{14mu} {flow}\mspace{14mu} {rate}} = {\frac{{\pi \left( {\rho \; V} \right)}_{b}{{NV}^{2}\left( \frac{U}{C} \right)}^{2}}{4\omega^{2}}{\sin^{2}\left( {2\alpha} \right)}{\tan^{2}\left( \frac{\pi}{N} \right)}}$

where (V)_(b)=bulk averaged mass flux

-   -   N=number of nozzles    -   V=Velocity leaving nozzles    -   (U/C)=Tip/Jet velocity ratio    -   ω=angular frequency    -   α=nozzle angle

To provide more flowrate at the optimum subtended angles while keepingthe rotor speed constant, a second row of axisymmetric nozzles, radiallyinboard of the first row can be used. FIG. 7 shows the arrangement of anouter row of nozzles, 86, and an inner row, 87, while maintaining theangle between the nozzle centerline and the plane normal to thecenterline of the rotor.

FIG. 8 shows that the areas 88, normal to the plane perpendicular to thecenterline of the turbine rotor, and the subtended angle 89, from axis89 a are closely similar for the nozzle first row and second row. Thesimilarity enables efficient conversion of the kinetic energy from bothrows of nozzles by the blades of the VPT. Each area 88 corresponds to across section, at a nozzle.

Another method to provide more flow at the optimum subtended angles isto provide a nozzle formed by two contoured surfaces with dividing vanesinserted between the surfaces to guide the expanding flow at the properangle. FIG. 9 shows cross sections 90 and 91, of the two contouredannuli 92 and 93 that incorporate such surfaces guiding vanes 101 extendbetween such surfaces 92 a and 93 a. Generally high pressure flow isprovided from a plenum, 94, formed by assembly of mating parts, andenters the nozzle passage, 95, at a generally inclined angle to theplane of the passage, typically 15-20 degrees. The flow expands to theexit, 96, where it leaves the nozzle at the same inclination andimpinges on turbine blades, 97. FIG. 10 shows the annuli 92 and 93having the nozzle surfaces. One of the surfaces, 100, is shown for thelower 93. The guiding vanes, 101, are shown to make an angle, 102, withthe plane perpendicular to the axis of the nozzle structure. This angleis typically between 15-20 degrees.

In the above, the medium is one of the following:

x₁) 1,1,12-Tetrafluoroethane, i.e., R134a

x₂) ii Difluoro-1,1-ethane, i.e., R152a

x₃) 1,1,1,2,3,3,3-heptafluoropropane, i.e., R227ea

x₄) 1,1,1,2,3,3-hexafluoropropane, i.e., R236ea

x₅) 1,1,1,3,3-pentafluoropropane, i.e., R245fa

x₆) 1,1,2,2,3-pentafluoropropane, i.e., R245ca

x₇) 1,1-dichloro-2,2,2-trifluoroethane, i.e., R123

x₈) CO2

x_(g)) CH4

x₁₀) propane

x₁₁) ethylene

x₁₂) propelene

x₁₃) water

x₁₄) nitrogen

x₁₅) mixtures where the above fluids comprise 50% or more of themixture,

Also disclosed herein are the contents of all claims.

1. A variable phase turbine comprising: i) nozzle means operable todischarge a fluid medium of liquid, supercritical fluid or a mixture ofliquid and gas with conversion of medium enthalpy to kinetic energy in adirected stream of a mixture of gas and liquid, supercritical fluid orpure gas, said directed stream characterized by the chemical compositionof the fluid medium and the thermodynamic conditions of the enthalpyconversion process, said nozzle means directing the flow at blade meansfor displacing said blade means, ii) the blade means configured tomaximize the conversion of the kinetic energy of said directed streaminto torque acting upon rotor means carrying said blades iii) said rotormeans to which said blades are attached transmitting torque to a shaftto which the rotor and a load are attached, iv) casing means configuredto confine and direct the medium and which contains bearings and sealsto enable the shaft to transmit the torque, and v) shroud meansconfigured and located to prevent liquid which has transferred kineticenergy to the blades from contacting the casing and from beingre-directed to contact the moving blades, causing losses in torque. 2.The turbine of claim 1 having pintle means to vary the flow area of thenozzle means by axial translation of said pintle means.
 3. The turbineof claim 1 characterized and configured with optimization in conformancewith a computer program characterizing the nozzle pressure profile toproduce the maximum conversion by the nozzle means of enthalpy for amedium of liquid or supercritical fluid to kinetic energy in a directedstream of a mixture of gas and liquid, supercritical fluid or pure gas.4. The turbine of claim 1 characterized and configured with optimizationin conformance with a computer program characterizing the nozzlepressure profile to produce minimum liquid droplet size in the nozzlemeans while optimizing kinetic energy for a mixture of gas and liquid.5. The turbine of claim 1 having a discontinuity in the profile of thewall of the nozzle means, said discontinuity causing any liquid on thewall to be directed into the flowing stream.
 6. The turbine of claim 1having two or more nozzle means with centerlines at different radii. 7.The turbine of claim 1 with nozzle means having plate dividers separatedby contoured surfaces enabling linear streamlines and fullcircumferential admission.
 8. The turbine of claim 1 characterized andconfigured with optimization in conformance with a computer programcharacterized the blading means to produce the maximum conversion of thekinetic energy to torque by a directed stream of a mixture of gas andliquid, supercritical fluid or pure gas.
 9. The turbine of claim 1having blades having an angular displacement of each blade leading edgefrom the perpendicular to the axis of the nozzle means of between 1degree to 15 degrees counter to the rotational direction.
 10. Theturbine of claim 1 wherein for a directed stream of a mixture of liquidand gas, the blading means has an initial section with a gradual angleoptimized to minimize the sum of momentum losses and friction losseswhen the stream impacts the blade surface.
 11. The turbine of claim 1wherein the case of a directed stream of a mixture of liquid and gas,the blading means is configured to increase the hydraulic diameter ofliquid flowing on the surface, thereby reducing friction losses.
 12. Theturbine of claim 1 wherein for the case of a directed stream of amixture of gas and liquid, the blade means is configured to configure atrajectory of liquid leaving the surface of the blades thereby toproduce a tangential component of the velocity relative to the shaftcenterline, causing the liquid to be separated from the gas phase and toenter a passage provided in the casing to capture the liquid.
 13. Theturbine of claim 1 wherein the case of a directed stream of a mixture ofgas and liquid, body structure is provided downstream of the rotor toprevent recirculation of the flow, preventing liquid from striking theblades.
 14. The turbine of claim 1 in combination with a) a shaftconnected to the turbine rotor, b) a shaft seal, and c) a generatorconnected to the shaft having bearings to support the shaft.
 15. Theturbine of claim 1 in combination with a) a shaft connected to theturbine rotor, b) a generator connected to the shaft that is cooled bythe medium, and c) bearings supporting the shaft that are lubricated bythe medium,
 16. The turbine of claim 1 in combination with a) a shaftconnected to the turbine rotor, b) a generator connected to the shaftthat is cooled by the medium, c) bearings supporting the shaft that arelubricated by the medium, and d) a self adjusting balance mechanism toreduce and control the axial force resulting from pressure differencesacross the rotor and the weight of the generator rotor and shaft. 17.The turbine of claim 1 in combination with a) a shaft connected to theturbine rotor, b) bearings supporting the shaft, c) a compressor(s)connected to the shaft.
 18. The turbine of claim 1 in combination witha) a shaft connected to the turbine rotor, b) bearings supporting theshaft, and d) a pump(s) connected to the shaft.
 19. The combination ofclaim 1 and a) a vertical shaft, b) an annular plenum that supplies themedium to the nozzle means, c) a passage for flow of the mediumsurrounding the generator, d) a port and insulated means to feedelectrical wires from the generator through the wall surrounding thegenerator, e) a means of separating the casing into components to enableaccess to the assembly comprised of the turbine, shaft and generator,and related parts, and f) support of the turbine, shaft and generatorassembly including a bottom plate, having pins to prevent rotationduring operation, enabling the assembly to be lifted for maintenancewithout undoing any mechanical fasteners.
 20. The turbine of claim 1where the medium is one of the following x₁) 1,1,12-Tetrafluoroethane,i.e., R134a x₂) ii Difluoro-1,1-ethane, i.e., R152a x₃)1,1,1,2,3,3,3-heptafluoropropane, i.e., R227ea x₄)1,1,1,2,3,3-hexafluoropropane, i.e., R236ea x₅)1,1,1,3,3-pentafluoropropane, i.e., R245fa x₆)1,1,2,2,3-pentafluoropropane, i.e., R245ca x₇)1,1-dichloro-2,2,2-trifluoroethane, i.e., x₈) CO2 x₉) CH4 x₁₀) propanex₁₁) ethylene x₁₂) propelene x₁₃) water x₁₄) nitrogen x₁₅) mixtureswhere the above fluids comprise 50% or more of the mixture.
 21. Variablephase turbine apparatus comprising, in combination a) a rotatably drivenload structure, defining an axis, b) confinement means forming a fluidflow passage extending generally axially and adjacent to said loadstructure, c) a turbine operatively connected to said load structure, totransmit rotary drive thereto, d) two-phase flow nozzle means receivingpressurized flow via said passage, and directing flow of fluid from saidpassage, expanded in the nozzle means, at the turbine to rotate theturbine, e) the nozzle means configured to expand flow consisting of twoor more of the following phases: i) gas ii) liquid iii) gas and liquidmixture iv) supercritical gas and liquid mixture, and with efficientconversion of enthalpy.
 22. The combination of claim 1 wherein said axisextends upright, and said nozzle means and turbine are located below theload level, fluid flowing downwardly in said passage to said nozzlemeans.
 23. The combination of claim 22 including structure extendingbelow said nozzle means and turbine to direct discharged fluiddownwardly away from said confinement means, said load structurecomprising an electrical generator having a rotor driven by saidturbine.
 24. The combination of claim 23 including means located abovesaid load structure and responsive to pressure of fluid flowing to saidpassage for exerting lifting force on the generator, during rotation ofsaid rotor.
 25. The combination of claim 24 including a tubular shaftextending axially and supporting the rotor for rotation, via shaftbearings, there being ducting for directing fluid flow from a pathassociated with said passage to the interior of said tubular shaft, viasaid bearings, for discharge below the turbine.
 26. The combination ofclaim 21 wherein said nozzle means includes a pintle controllablyaxially movable within a tapered nozzle bore and relative to a nozzlethereto, to selected position for controlling the particle size of fluidpassing through the nozzle means, and to control slip at inlet regionsof the nozzle means.
 27. The combination of claim 26 wherein said nozzlemeans includes multiple nozzles circularly spaced about said axis, andangled downwardly toward turbine blades, the nozzle having inlets belowsaid passage.
 28. The combination of claim 26 including actuator meansto control pintle positioning within the nozzle bore, and meansincluding a computer programmed cooling to control said actuator meansso as to maximize said slip, for a selected fluid phase flow.
 29. Thecombination of claim 27 wherein said multiple nozzles are arranged intwo concentric rings for enhancing nozzle fluid discharge drive momentexerted on turbine blading.
 30. The combination of claim 29 wherein saidtwo concentric rings are located below said load.
 31. The combination ofclaim 21 wherein said nozzle means is or are a two-phase nozzle, ornozzles.
 32. The combination of claim 21 wherein the load is acompressor.
 33. The method of operating the turbine apparatus of claim 1which includes f) directing the flow through said nozzle means, g)adjusting said nozzle means to compensate for conversion of the flowfrom a first of said phases to a second of said phases, whereby sizes offlow particles leaving the nozzle means are minimized in said first andsecond phases.
 34. The method of claim 33 including controlling saidadjusting by provision of and operation of a programmed computer. 35.The method of claim 34 wherein said controlling of said adjustingincludes providing a tapered pintle or pintles in a tapered bore orbores of said nozzle means, to extend lengthwise therein, andcontrollably and adjustably displacing said pintle or pintles lengthwisein said bore or bores to minimize said particle sizes.
 36. The method ofcontrolling the operation of a turbine having a nozzle or nozzle towhich pressurized fluid is supplied, that includes the step: adjustingnozzle flow through configuration, as a function of input fluid phasecomposition, to minimize particle size while optimizing kinetic energyof nozzle discharge incident on turbine blades.
 37. The turbine of claim1 wherein the nozzle means is characterized and configured by slipmaximized at the inlet region or regions of the nozzle means.